US9737932B2 - Method of manufacturing a component covered with an abradable coating - Google Patents

Method of manufacturing a component covered with an abradable coating Download PDF

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US9737932B2
US9737932B2 US14/432,994 US201314432994A US9737932B2 US 9737932 B2 US9737932 B2 US 9737932B2 US 201314432994 A US201314432994 A US 201314432994A US 9737932 B2 US9737932 B2 US 9737932B2
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blank
rolling
housing
abradable
abradable material
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US20150231699A1 (en
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Laurent Ferrer
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/18—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by using pressure rollers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/18—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by using pressure rollers
    • B22F2003/185—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by using pressure rollers by hot rolling, below sintering temperature
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor

Definitions

  • the present disclosure relates to a method of fabricating a part covered by an abradable coating.
  • machines have portions that, when moving, rub against other portions or run the risk of rubbing against other portions.
  • certain machines comprise a movable part that rotates about an axis, with a portion of the movable part rubbing against another part.
  • turbomachines whether terrestrial or for aviation, such as turbojets or turboshaft engines
  • turbomachines that have a rotor with movable blades that, in their rotary movement, rub against the inside face of a stator casing surrounding them.
  • the solution presently in use consists in bringing the movable blades as close as possible to the casing and in covering the casing with a coating of soft material facing the blades.
  • This material is abradable, which means that it has the property of being easy for the tips of the movable blades to dig into in the event of contact.
  • a blade is practically undamaged when it rubs against the abradable material and the space between the tip of the blade and the inside surface of the casing is optimized by adjusting this space to a minimum over time.
  • strip portions of an abradable material are fabricated, each strip portion is then stuck to the casing in order to form a complete abradable strip.
  • Such a method is lengthy and expensive.
  • using adhesive presents numerous constraints: cleaning the surfaces that are to receive the adhesive, problems of contamination of the cleaned surfaces, poor adhesion, etc.
  • the mechanical stresses generated during fabrication of the strip portions of abradable material and while they are being stuck into place lead during operation to these strip portions becoming unstuck from the surface of the casing and/or to cracking and to premature deterioration of the strips in service.
  • the present invention seeks to remedy these drawbacks, at least in part.
  • the present description provides a method of fabricating a part covered in an abradable coating, the method comprising the following steps:
  • the blank that is provided is advantageously rough, i.e. the blank has not yet been shaped while hot (forging, rolling, . . . ).
  • the housing may already have been shaped while hot and/or machined.
  • the rolling that is performed serves to apply hot compression locally to the abradable material.
  • this is unidirectional hot compression acting normally to the inside surface of the blank.
  • This hot compression serves to sinter and compact the abradable material and causes it to adhere to the blank by diffusion welding.
  • the hot compression applied by the rolling suffices to sinter and compact the abradable material and to cause it to adhere to the blank, and the fabrication method does not have any hot compression step before or after the rolling step.
  • Such a method makes it possible to ensure that the particles of the abradable material are well compacted and that they cohere together well. Furthermore, with the temperatures and the pressures involved during rolling, the particles adhere well to the blank and the welding interface between the material of the blank presents few or no pores. The risk of the abradable coating subsequently becoming unstuck is thus reduced.
  • the blank and the abradable material may be shaped as close as possible to the dimensions of the final part, e.g. using mandrels that are straight or mandrels that are shaped.
  • the housing opens out into the surface of the blank via one or more openings. During rolling, pressure is exerted on the abradable material through the opening(s).
  • said housing is filled with the abradable material via the opening(s) during the filling step (step B) and the opening(s) is/are closed hermetically with a sheath, prior to the rolling step (step C).
  • the method includes the following steps:
  • steps D to F are performed after above-mentioned step A and before above-mentioned step B, with step E relating to step B.
  • the rolling step C comprises a preheating first step C1 during which the blank is heated to a rolling temperature T, with the sintering of the abradable material taking place, at least in part, during this first step, and a second step C2 during which the blank and the abradable material are rolled together at the rolling temperature T.
  • the particles of abradable material become mutually agglomerated by sintering with given porosity, and this takes place while the blank is being preheated to the rolling temperature. Thereafter, during the rolling operation proper, the abradable material deforms as a result of the pressure exerted while hot (i.e. at the rolling temperature T).
  • the dilution zones associated with the diffusion welding between the powder particles
  • the residual pores after sintering and compacting decrease, or even disappear. Recrystallization mechanisms in the abradable material may even be triggered, thereby further improving the uniformity of the abradable coating.
  • the rolling temperature (and more generally the thermomechanical cycle of the part) should be defined as a function of the narrowest forgeability range taking into account the adiabatic heating and the range that leads to the desired microstructures for the materials under consideration.
  • the maximum temperature should be at the overheating or burning limit for one of the materials being shaped and the minimum temperature should be at the limit of microstructural damage to one of the materials.
  • the rolling temperature T may lie in the range 600° C. to 1350° C.
  • EN X12CrNiMoV12 or for a steel known as EN X4NiCoNb38 the rolling temperature T may lie in the range 750° C.
  • the rolling temperature T may lie in the range 850° C. to 1250° C. If the material is a titanium alloy, the rolling temperature T may lie in the range 700° C. to 1150° C.
  • the rolling temperature T may lie in the range 700° C. to 1050° C., and it is advantageous to use a temperature T of about 950° C.
  • the rolling temperature T may lie in the range 1050° C. to 1150° C., and a temperature T of about 1100° C. is used advantageously.
  • the abradable material is deposited as a plurality of layers of different kinds.
  • the abradable material in its powder form comprises base particles that, after rolling (step C), constitutes the matrix of the abradable coating, together with secondary particles that facilitate fragmentation of the abradable coating.
  • the secondary particles facilitate fragmentation of the abradable coating when rubbing against a moving part, and thus serve to adjust the clearance between the moving part and the coating.
  • organic secondary particles may be introduced in the particle mixture. Such particles decompose during the rolling operation so as to form gas-filled pores. These pores facilitate fragmentation of the coating.
  • the abradable material also comprises hard, wear-inducing particles that serve in operation to polish the moving parts, to some extent.
  • the housing presents side faces that are concave (towards the inside of the housing). This serves to hold the abradable coating captive without generating residual stresses therein or at least to distribute the stresses at the interface between the abradable coating and the substrate, thereby limiting separation.
  • the housing is a groove defined by an inside wall, two side walls surrounding the bottom wall, and two outer lips situated extending the side walls towards the center of the groove in such a manner that the groove presents a generally C-shaped profile in cross-section.
  • a housing serves to hold the abradable coating firmly captive, in particular because of the outer lips that cover the coating in part and that retain it.
  • housings of other shapes with the compression during rolling serving to fill the entire housing, even if it is of a complex shape.
  • the housing may be deformed so as to hold the abradable coating captive even better.
  • the blank is formed by hot rolling at least two sub-portions together, this rolling together of the sub-portions and the step of rolling the blank and the abradable material together (above-mentioned step C) being performed simultaneously as a single operation.
  • the blank and/or the coating of abradable material is/are machined in order to obtain the final part.
  • quality heat treatment is applied to the part as a whole, i.e. heat treatment for imparting to the part characteristics that it needs in use.
  • the fabricated part is a turbomachine casing having a radially inner face, at least a portion of this face being covered by the abradable coating.
  • said housing is provided in the radially inner face of the casing.
  • FIG. 1 is a cross-section showing a blank for a part, which blank includes a housing opening out into the surface of the blank.
  • FIG. 2 shows the FIG. 1 blank, with a sheath put into place thereon.
  • FIG. 3 shows a step of filling the housing with an abradable material in powder form.
  • FIG. 4 shows a step of rolling of the blank and the abradable material together.
  • FIG. 5 shows a machining step
  • FIG. 6 is a figure analogous to FIG. 3 , showing a step of filling the housing with another abradable material.
  • FIG. 7 is a figure analogous to FIG. 3 , showing a step of filling the housing with an abradable material that is deposited as a plurality of layers.
  • FIG. 8 is a figure analogous to FIG. 4 , showing a rolling step.
  • FIGS. 1 to 5 show various steps in an implementation of the method of fabricating a part 1 with an abradable coating 50 .
  • the part 1 is shown in FIG. 5 .
  • a portion of the abradable coating 50 forms a layer 55 at the surface of the part 1 .
  • the layer 55 slightly projects outwards from the remainder of the part 1 .
  • the part 1 is a turbomachine casing, e.g. a turbojet compressor casing.
  • the casing has an abradable coating 55 against which movable parts 60 rub (see FIG. 5 ). These movable parts 60 are blades.
  • the free surface 35 on which the abradable coating 55 is formed is the radially inner face of the casing. It is a surface of generally cylindrical shape, centered on the axis of rotation of the turbomachine rotor.
  • the invention may be applied to parts other than a turbomachine casing.
  • a blank 10 is initially provided for the part.
  • the blank 10 shown in FIG. 1 , has a housing 20 .
  • the housing 20 opens out into the surface 15 of the blank 10 via an opening 25 .
  • This opening 25 is continuous. It could equally well be discontinuous, i.e. it could be made up of a plurality of sub-openings.
  • the housing 20 is a groove that extends in a direction perpendicular to the section plane of the figures.
  • the shape of the housing 20 is preferably selected in such a manner as to hold captive the abradable coating 50 that is described below.
  • the maximum section of the housing 20 in a plane parallel to the surface 15 is situated at a non-zero distance from that surface.
  • the housing 20 presents at least one converging portion.
  • the abradable material 50 that fills the housing 20 (see below), once it is in the form of a single-piece block, is held mechanically in the housing 20 .
  • the housing 20 is a groove defined by a bottom wall 21 , two side walls 22 surrounding the bottom wall, and two outer lips 23 extending the side walls and projecting towards the center of the groove.
  • the groove thus presents, in cross-section, a profile that is generally C-shaped.
  • the opening 25 is defined between the outer lips 23 .
  • the side surfaces of the groove, as defined by the side walls 22 are concave towards the inside of the groove.
  • the housing 20 is made by machining in the blank 10 .
  • the blank 10 Prior to machining, the blank 10 may already have an indentation at the location where the housing 20 is to be machined. This indentation may be made when shaping the blank 10 .
  • the housing 20 is cleaned.
  • the opening 25 of the housing 20 is covered with a sheath 30 that comprises vacuum orifices 31 and filling orifices 32 .
  • the sheath 30 is fastened to the entire periphery of the opening 25 on the edges of the lips 23 of the housing.
  • this fastening may be performed by welding.
  • the size of the sheath 30 and the positions of the welds may be optimized to avoid any leakage.
  • the sheath 30 is made of a material that is sufficiently flexible and ductile and of thickness that is sufficiently small to deform under the effect of the pressure P that is applied during rolling (see below).
  • the sheath 30 closes the opening 25 in leaktight manner with the exception of the orifices 31 and 32 .
  • a vacuum is then established inside the housing 20 (i.e. in the closed space defined by the housing 20 and the sheath 30 ), while the housing 20 is being filled with an abradable material 50 in powder form.
  • the abradable material 50 is in the form of a collection of separate particles makes such filling possible.
  • the abradable material 50 is constituted by a collection of particles.
  • the term “particle” is used to mean an element of small size that may in particular be in the form of a substantially spherical grain or in a shape that is longer in one dimension (of the fiber type), or in two dimensions (of the plate type). All or most of the particles are made of a material that is sinterable, i.e. a material suitable for diffusing from one particle to an adjacent particle when the particles are compacted at high temperature, so that bonds are created between the particles: the material is then sintered. During sintering, the material constituting the particles does not necessarily melt. In a sintered material, it is possible for pores to remain. If the material is compacted at even higher temperatures, then the particles are deformed, and then diffusion welded, and as a result empty pores progressively disappear.
  • the abradable material 50 in its powder form may be constituted by a base powder 51 . It may be a single powder or it may be a mixture of powders. After rolling, the base powder 51 constitutes the matrix of the abradable coating 55 .
  • the abradable material 50 is constituted by a mixture based on metal powders such as powders of a special alloy based on Ni or based on Fe.
  • the abradable material is selected as a function of the required properties, in particular thermal properties.
  • the abradable material 50 is constituted by secondary particles 52 that are mixed with the base powder, thereby facilitating fragmentation of the abradable coating 55 in operation.
  • These secondary particles 52 may be particles that are organic, inorganic, metallic, intermetallic, etc., whose chemical interaction with the base of the abradable material is weak.
  • secondary particles 52 it is possible to use oxides, in particular based on carbon, such as for example powders of pure carbon, carbon fibers, or carbides (SiC, TiC, WC, etc.), particles based on boron such as for example borides or borates (TiB 2 , SiB 2 , Laves phases, etc.), nitrides, and/or microbeads of an organic resin having a vaporization point slightly lower than the rolling temperature.
  • These secondary particles 52 facilitate separation of pieces of abradable coating 55 when the movable part 60 with which the part 1 interacts moves past.
  • the secondary particles 52 may have two modes of action.
  • particles that are inorganic, metallic, or intermetallic e.g. oxides, carbon-based particles, boron-based particles, and/or nitrides.
  • the secondary particles 52 are hollow and/or decompose, thereby releasing gas during rolling, thus creating pores that weaken the structure of the matrix.
  • microbeads that are metallic and/or made of organic resin, having a vaporization point that is slightly lower than the rolling temperature.
  • the microbeads may be hollow resin beads or hollow metal beads, containing a vacuum or gas, or hollow metal beads having resin inside.
  • the secondary particles 52 may also be “wear-inducing”, i.e. they may be selected for their properties of resistance to wear. In operation, such particles then serve to slightly polish the moving parts.
  • particles that are inorganic, metallic, or intermetallic, and for example oxides, carbon-based particles (e.g. carbon powder, carbon fibers, carbides), particles based on boron (e.g. borides or borates), and/or nitrides.
  • the abradable material in powder form
  • the abradable material is deposited as a plurality of layers 56 , 57 , these layers being of different kinds.
  • Two layers are said to be of different kinds when the two layers are made of different materials, or when one layer is constituted by a mixture of materials and another layer is constituted by a mixture of the same materials, but in different proportions.
  • the housing 20 is filled by a stack of layers 56 , 57 , each layer having a specific composition.
  • the composition of each layer depends on the functions desired for the layer.
  • the first layer 56 i.e. the layer that is closest to the bottom 21 of the housing 20
  • the second layer 57 i.e.
  • the larger that is to come into contact with the moving part 60 is constituted by way of example by an alloy having high refractory content, and possibly high secondary particle content, so as to enhance the adaptability and the thermal stability of the surface over time.
  • the casing material is a steel known as EN X12CrNiMoV12
  • depositing a first layer 56 of powder based on Fe serves to obtain better diffusion welding of the particles of powder on the substrate. This welding improves the strength of the abradable material.
  • the fact of adding a final layer 57 based on Ni powders provides the surface of the abradable coating with greater ability to withstand high temperatures.
  • a first method consists in modifying the mixture of particles being deposited progressively as the housing fills (filling may be optimized with the number of filling orifices) prior to establishing a vacuum.
  • a second method consists in filling the underlayers one by one by depositing an intermediate sheet (e.g. a metal sheet) between two underlayers, and in finishing by depositing the sheath 30 before establishing the vacuum.
  • a third method consists in spraying the abradable material 50 while hot or cold into the housing 20 via the opening 25 in order to obtain mechanical cohesion in successive layers prior to welding the sheath 30 and establishing the vacuum.
  • FIG. 3 shows this step.
  • the volume defined by the wall of the housing 20 and by the sheath 30 is strictly greater than the volume of the housing 20 , where the volume of the housing 20 is defined by the wall of the housing 20 and a plane extending the surface 15 into which the opening 25 opens out.
  • the blank 10 and the abradable material 50 are rolled together so as to sinter and compact the abradable material and so as to cause it to adhere to the blank, in order to obtain an abradable coating 55 .
  • Rolling serves to apply a pressure P that is higher than atmospheric pressure to the outside face of the sheath 30 .
  • the sheath 30 thus deforms under the effect of stress (unidirectional stress acting normally to the surface 15 in this implementation).
  • This stress subjects the abradable material 50 to a compression in the housing 20 (the abradable material 50 also being stressed by the walls of the housing 20 ), the abradable material 50 also being subjected to a temperature T, which is generally higher than 150° C., so that sintering takes place between the particles of the abradable material 50 and this material becomes compacted in the housing 20 .
  • T which is generally higher than 150° C.
  • hot ring rolling technique In order to perform hot rolling, it is possible to use a hot ring rolling technique, or the like.
  • An example of the hot ring rolling technique is described in the publication entitled “A summary of ring rolling technology. I—Recent trends in machines, processes, and production lines” bit. Mach. Tools 14 Manufact. Vol. 32, No. 3, 1992, pp. 379-398, by the authors E. Eruc and R. Shivpuri.
  • it is possible to use two rotary mandrels that compress the blank 10 and the abradable material 50 one of the mandrels following the surface of the blank in which the opening 25 of the housing 20 is rotated so as to exert pressure on the abradable material 50 through the opening 25 .
  • two rotary mandrels (of vertical axes in FIGS. 4 ) 71 and 72 compress the blank 10 and the coating 50 and reduce the thickness of the blank 10 by increasing its diameter.
  • One of the mandrels 72 is in contact with the surface 15 and with the sheath 30 and exerts a pressure P thereon.
  • Two cones (not shown and having axes that are horizontal in the figure) may be used for limiting the increase in the height of the blank 10 that can result from the action of the mandrels 71 , 72 . It is then possible to perform annealing heat treatment. This produces a circular part in the shape of a body of revolution having an abradable coating 55 .
  • the rolling is performed hot at a temperature C higher than the temperature at which all of the pores in the abradable material 50 are resorbed.
  • this temperature T lies in the range 700° C. to 1300° C.
  • the sintering and the compacting of the abradable material 50 begin during the heating during which the blank is maintained at the temperature T for a holding time, without pressure being applied. Compacting terminates during the rolling step proper.
  • the pressure P exerted by the roller 72 on the abradable material 50 through the opening 25 is a function of the flow stress specific to the abradable material at the rolling temperature.
  • the flow stress of the abradable material is much less than that of the substrate, thereby enabling the layer of abradable material to be better deformed.
  • the abradable material 50 is sintered and compacted and occupies a volume (referred to as its final volume) that is less than its initial volume, because of the compacting and the sintering that have taken place between the particles of the material.
  • the surface 15 of the blank (in particular at its lips 23 ), and the side edges of the abradable coating 55 are machined in such a manner as to obtain a strip of abradable coating 55 that slightly projects from the remainder of the free surface 15 of the part 10 .
  • the movable part 60 rubs against this strip of abradable coating 55 in operation until the clearance between the coating 55 and the part 60 (drawn in dashed lines) is optimized, as shown in FIG. 5 .
  • the blank 10 is made by hot rolling of at least two sub-portions 11 and 12 together.
  • the first portion 11 may be made of titanium alloy while the second portion 12 is made of steel or of a nickel-based alloy. These two portions 11 and 12 may be separated by an anti-diffusion intermediate film 13 .
  • the first portion 11 which constitutes the load-bearing structure made of titanium alloy, is protected from risks of titanium fire by the second portion 12 .
  • the housing 20 that receives the abradable coating 55 is formed in the second portion 12 .
  • the portions 11 , 12 , and 13 are rolled together, and advantageously they are rolled together while simultaneously rolling together the portion 12 and the abradable coating 55 , in a single common operation.
  • a quality heat treatment may be applied to the part 1 .

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/432,994 2012-10-05 2013-10-01 Method of manufacturing a component covered with an abradable coating Active 2034-08-30 US9737932B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1259518 2012-10-05
FR1259518A FR2996476B1 (fr) 2012-10-05 2012-10-05 Procede de fabrication d'une piece couverte d'un revetement abradable
PCT/FR2013/052326 WO2014053761A1 (fr) 2012-10-05 2013-10-01 Procede de fabrication d'une piece couverte d'un revetement abradable

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150266093A1 (en) * 2012-10-05 2015-09-24 Snecma Method for incorporating abradable material into a housing by isostatic pressing

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102076922B1 (ko) * 2015-04-23 2020-02-12 더 팀켄 컴퍼니 베어링 구성요소를 제조하는 방법

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03202433A (ja) 1989-12-29 1991-09-04 Furukawa Electric Co Ltd:The 金属―セラミックス複合材料の製造方法
US5663276A (en) * 1993-06-15 1997-09-02 Nippon Petrochemicals Company, Limited Wholly aromatic polyester, composition thereof, and molded article made therefrom
GB2315778A (en) 1996-08-01 1998-02-11 Smith International Composite constructions with oriented microstructure.
US20040111892A1 (en) 2001-10-08 2004-06-17 Greene Robert L. Lead-free bearing
US20060068214A1 (en) 2004-09-30 2006-03-30 Gigliotti Michael F X Erosion and wear resistant protective structures for turbine components
CN1896451A (zh) 2006-06-07 2007-01-17 吉林大学 仿生孕镶金刚石钻头及其制造方法
US20070092394A1 (en) 2005-10-26 2007-04-26 General Electric Company Supersolvus hot isostatic pressing and ring rolling of hollow powder forms
US20070258844A1 (en) * 2006-05-08 2007-11-08 Huntington Alloys Corporation Corrosion resistant alloy and components made therefrom
EP2112326A1 (de) 2008-04-23 2009-10-28 Snecma Gehäuse eines Turbotriebwerks mit einer Vorrichtung zum Schutz vor Instabilität bei Kontakt zwischen dem Gehäuse und dem Rotor
FR2935623A1 (fr) 2008-09-05 2010-03-12 Snecma Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
CN101801567A (zh) 2007-07-31 2010-08-11 费德罗-莫格尔公司 耐磨无铅合金轴衬及其制造方法
US20120114971A1 (en) 2007-01-05 2012-05-10 Gerd Andler Wear resistant lead free alloy sliding element method of making
US20120174644A1 (en) * 2009-09-09 2012-07-12 Siemens Vai Metals Technologies Sas Leveling machine with multiple rollers

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2461448C1 (ru) * 2011-05-27 2012-09-20 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Способ изготовления прирабатываемого уплотнения турбины со столбчатой структурой
RU2461449C1 (ru) * 2011-06-27 2012-09-20 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Способ изготовления прирабатываемого уплотнения турбины с многослойной оболочкой

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03202433A (ja) 1989-12-29 1991-09-04 Furukawa Electric Co Ltd:The 金属―セラミックス複合材料の製造方法
US5663276A (en) * 1993-06-15 1997-09-02 Nippon Petrochemicals Company, Limited Wholly aromatic polyester, composition thereof, and molded article made therefrom
GB2315778A (en) 1996-08-01 1998-02-11 Smith International Composite constructions with oriented microstructure.
US20040111892A1 (en) 2001-10-08 2004-06-17 Greene Robert L. Lead-free bearing
US20060068214A1 (en) 2004-09-30 2006-03-30 Gigliotti Michael F X Erosion and wear resistant protective structures for turbine components
US20070092394A1 (en) 2005-10-26 2007-04-26 General Electric Company Supersolvus hot isostatic pressing and ring rolling of hollow powder forms
EP1779946A1 (de) 2005-10-26 2007-05-02 General Electric Company Isostatisches Supersolvus-Heisspressen und Ringwalzen von Hohlpulverformen
US20070258844A1 (en) * 2006-05-08 2007-11-08 Huntington Alloys Corporation Corrosion resistant alloy and components made therefrom
CN1896451A (zh) 2006-06-07 2007-01-17 吉林大学 仿生孕镶金刚石钻头及其制造方法
US20120114971A1 (en) 2007-01-05 2012-05-10 Gerd Andler Wear resistant lead free alloy sliding element method of making
CN101801567A (zh) 2007-07-31 2010-08-11 费德罗-莫格尔公司 耐磨无铅合金轴衬及其制造方法
EP2112326A1 (de) 2008-04-23 2009-10-28 Snecma Gehäuse eines Turbotriebwerks mit einer Vorrichtung zum Schutz vor Instabilität bei Kontakt zwischen dem Gehäuse und dem Rotor
FR2935623A1 (fr) 2008-09-05 2010-03-12 Snecma Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
US20110268566A1 (en) * 2008-09-05 2011-11-03 Snecma Method for the manufacture of a circular revolution thermomechanical part including a titanium-based load-bearing substrate lined with steel or superalloy, a turbomachine compressor housing which is resistant to titanium fire obtained using this method
US20120174644A1 (en) * 2009-09-09 2012-07-12 Siemens Vai Metals Technologies Sas Leveling machine with multiple rollers

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
English language translation of Second Office Action and Search Report issued Jan. 3, 2017, in corresponding Chinese Application No. 201380056773.5 (8 pages).
Search Report mailed on Jan. 17, 2014, in corresponding International Application No. PCT/FR2013/052326 filed on Oct. 1, 2013 (2 pages).

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150266093A1 (en) * 2012-10-05 2015-09-24 Snecma Method for incorporating abradable material into a housing by isostatic pressing
US9943908B2 (en) * 2012-10-05 2018-04-17 Safran Aircraft Engines Method for incorporating abradable material into a housing by isostatic pressing

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RU2015116598A (ru) 2016-11-27
EP2903763B1 (de) 2018-09-26
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CA2886926C (fr) 2020-07-14
FR2996476A1 (fr) 2014-04-11
CN104755198A (zh) 2015-07-01
BR112015007287B1 (pt) 2020-04-07
WO2014053761A1 (fr) 2014-04-10
BR112015007287A2 (pt) 2017-07-04
FR2996476B1 (fr) 2015-02-13
RU2646656C2 (ru) 2018-03-06
CN104755198B (zh) 2018-03-16
CA2886926A1 (fr) 2014-04-10

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